By Walt Truszkowski, Harold Hallock, Christopher Rouff, Jay Karlin, James Rash, Michael Hinchey, Roy Sterritt
This publication presents an in-depth dialogue of self reliant and autonomic platforms, their interdependencies, variations and similarities. present and pending concerns in those evermore more and more very important matters are highlighted and mentioned. strategies, principles and reports are explored with regards to real-life NASA platforms in spacecraft keep an eye on and within the exploration area.
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Extra resources for Autonomous and Autonomic Systems: With Applications to NASA Intelligent Spacecraft Operations and Exploration Systems
Some of these functions are already largely performed autonomously onboard. A working deﬁnition of the diﬀerence between autonomy and automation was supplied in Chap. 1. A description of the current state of the art of onboard autonomy/automation will be supplied in Chap. 3. Next, we will brieﬂy discuss each of the steps in the overall spacecraft operations process. 1 Planning and Scheduling Especially for low earth orbit (LEO) missions, the ground system P&S function traditionally has been responsible for generating a detailed desired optimized timeline of spacecraft activities, sometimes (as in the case of Hubble Space Telescope (HST)) based on rather complex predictive modeling of the spacecraft’s environment and anticipated behavior.
This ground system function will become steadily more automated via COTS tools. 11 Engineering Data Analysis/Calibration Traditionally, nearly all spacecraft engineering analysis and calibration functions (with the exception of gyro drift-bias calibration and, for the small explorer (SMEX) missions, magnetometer calibration) have been performed on the ground. 2 Flight Software 31 communications-margins evaluations, etc. Often the work in question has been iterative and highly manually intensive.
Fourth, the process may be performed onboard in order to reduce demand on a limited resource. For example, downlink bandwidth is a valuable, limited quantity on most missions, either because of size/power constraints on spacecraft antennas/transmitters, or because of budget limitations on the size of the ground antenna. In such cases, FSW may be used to compress the output from payload instruments or prune excessive detail from the engineering telemetry stream to accommodate a smaller downlink data volume.